Contbol mechanism



Mmh s, 192s.

E. H. VAN VALKENBERG CONTROL MECHANISM Filed 00?.. 23, 1926 gmzanor Ebel' H. Van Va/'enbe/'y MMM W @Hamai Patented Mar. "6, 1928.1

UNITED STATES PATENT OFFICE.

:EBER HARLEY VAN VALKENBERQoF yineiinnsroa'r, PENNSYLVANIA, AssIGNon or ONE-HALE 'ro OSCAR SILVERSTEIN, or sroKANE, WASHINGTON.l

coN'rRoL MEGHANISM.

Application filedv October 23, 1926. Serial No. 143,623.

My present invention relates to an improved control mechanism for steering and controlling the movementsot aeroplanes.

The primary object of the invention is the provision of manually and pedal operated mechanism by means of which the vertical steering rudder, the elevators or horizontal rudders, and the ailerons or wing'flaps of the main Supporting plane or wing may with facility and accuracy be controlled and manipulated for accomplishing the necessary movements of the aeroplane while in flight.

The invention consists in certain novel combinations and arrangements of parts in# volving the usual dual control lever vor stick, and pedal devices Ain connection with the operating cables and levers as will be hereinafter morefully set forth and claimed.

In the accompanying drawing, I have illustrated one complete example of the physical embodiment of my invention where- `in the parts are combined and arranged according to the best mode I have so far devised for the practical application of the principles of my invention.

The figure of drawingis a' perspective View showing the general assembly and arrangement of parts ofl the control mechanism.

The drawing shows a sufficient number of part to indicate the arrangement of the control mechanism and portions of the supporting plane or top wing 1 of an aeroplane are shown with Vthe right and left ailerons 2 and 3 hinged at the rear edge of the supporting plane 1, these being used for lateral control of the plane in usual manner.

At the rear or tail end of the aeroplane,

i the right and left elevators as 4 and 5 are shown and used as horizontal rudders for regulating the pitch and rate of ascentv and descent of the machine or aeroplane.

Between the duplicate horizontal rudders 4 and 5, the vertical rudder 6 is shown for lateral steering of the aeroplane.

The ailerons are controlled from the control stick or dual lever 7 which of course is located in position for ready access of the aviator, and is pivoted at 8 on a rock shaft 9 which extends fore and aft or longitu dinally of the aeroplane and is journaled in brackets 10. Bymeans of the stick or lever 7 the rockshaft 9 may be rocked in its bear-r ings, Y

of rock arms 11 and 12 to which the duplex v and the shaft is providedwith apair cables 13 and V14are connected; These i cables pass around guide pulleys 15 located at suitable points ini-the fuselage `or body of4 the aeroplane, and the cables extend outwardly towardthe outer ends of the supporting wing, abovethe upper surface of the wing. wing or plane 1 are provided bell crank members 1G pivoted at 17 to the Vsupporting plane, and the dual cables 13 and 14 atftheir outer ends are connected to these bell crank Y levers. Each aileron has a link as 18 pivoted thereto at 19, and each link isconnected to one of thebell crank levers 16. It will beapparent that by swinging the. stick 7 laterally the ailerons maybe tilted upwardlyor downwardly with relation to the rear edge of. the supporting planeor wing 1,:and in order to insure simultaneous and synchronyous movement of the ailerons, a cross cable 20 extending transversely of the aeroplane connects a pair' of the bell cranklevers 16.

The horizontal rudders or elevators 4 and 5 are also controlled from the dual stick 7 and for this purpose the latter is oscillated on its pivot S.

` At the'rear of the longitudinally eXtending rock shaft 9, a transversely extending rock shaft 21 is journaled in bearing frames or brackets 22, and this rock shaft 21 has a rock arm 23 that is` connected by the pitman Near the opposite ends4 ofthe Y 24 with the dual stick 7. A universal joint y 25 is provided in the pitinan to facilitate the movement of the control stick 7 with relation to the rock arm 23 of rock shaft 21.

The rock shaft 21 for the elevators is provided with spaced pairs of diametrically arranged crank arms 26 and27 located at opposite sidesv of the lever arm 23. Each pair of crank arms is providedwith dual cables as 28 and 29 which extend rearwardly and are connected at 30 on the upper and lower faces of the elevators 4 and 5. From this description, it will be apparent that by swinging the control stick 7 on its pivot 8, the Aelevators or horizontal rudders 4 and 5 may be tilted in manner similar to the magear connections are provided between the pedals and the levers. From the levers 33 and 34 the respective cables 36 and 37 extend rearwardly oi the aeroplane and are connected to the lever arms 38 projecting laterally at opposite sides ot the vertical rudder By pressing forward on the right pedal 31, the rudder G will be turned toward the right, and of course by pressing forward on the pedal 32, the rudder 6 may be turned to the left for maneuvering the aeroplane.

By this combinationand arrangement of operating levers, cable connections and rock shafts, it will be apparent that I have provided a control mechanism which insures facility, convenience, accuracy and reliability in controlling the essential parts of the aeroplane.

Having thus fully described my invention, what I claim as new and desire to secure by Letters Patent, is

1. In an aeroplane the combination with hinged ailerons and horizontal rndders, of a pair of angnlarly disposed rock shafts having crank arms thereon. a pivoted control stick for operating one shaft, and an operative connection between the said stick and the other rock shaft, of cables connectingr the crank arms of the second shaft to the rndders, a pair of hell crank levers for each aileron, pivoted links connecting said levers and ailerons, and dual cables connecting, said levers and crank arms to the first shaft.

Q. llhe combination in an aeroplane with hinged ailerons, ol a rock shaft and control stick thereon, a pair of' rock arms on said shaft, dnalcables connected to each rock arm, a pair ol hell crank levers for each aileron to which said cables are connected, and pvoted links connecting,r said bell crank levers and ailerons.

3. The combination with a supporting plane and its hinged ailerons, of a rock shaft having a pair ot' rock arms and a control stick for said shaft, dual cables attached to each rock arm and guide pulleys for said cables, a pair of bell crank levers for each aileron pivoted on the main plane and connccted with said dual cables, a cross cable connecting a pair of bell cranks, and pivoted links connecting said bell cranks `and said ailerons.

In testimony whereof I allix my sigx'latnre.

EBER HARLEY VAN VALKENBERG. 

